CA2368288A1 - Laser shock peening integrally bladed rotor blade edges - Google Patents
Laser shock peening integrally bladed rotor blade edges Download PDFInfo
- Publication number
- CA2368288A1 CA2368288A1 CA002368288A CA2368288A CA2368288A1 CA 2368288 A1 CA2368288 A1 CA 2368288A1 CA 002368288 A CA002368288 A CA 002368288A CA 2368288 A CA2368288 A CA 2368288A CA 2368288 A1 CA2368288 A1 CA 2368288A1
- Authority
- CA
- Canada
- Prior art keywords
- laser
- spots
- elliptical shaped
- laser spots
- blades
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Optics & Photonics (AREA)
- General Engineering & Computer Science (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A method for laser shock peening rotor blade (108) leading and trailing edges (LE, TE) of gas turbine engine integrally bladed rotors and disks that are not blocked by other rows of blades. The method includes continuously firing a stationary laser beam (102), which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges (LE, TE) of the blade (108), with the laser beam (102) aimed at an oblique angle (110) with respect to a surface of the edge such that laser pulses form overlapping elliptical shaped laser spots (60). In the exemplary embodiment of the invention, the elliptical shaped laser spots (60) have an overlap of about 50% and are on the order of 11.7 mm by 4 mm in diameter. Another method is for laser shock peening rotor blade leading and trailing edges (LE, TE) of gas turbine engine integrally bladed rotors and disks that are blocked by other rows of blades.
The method includes continuously firing the stationary laser beam (102), which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges (LE, TE) of the blade (108), with the laser beam (102) compoundly angled such that it is aimed at a first oblique angle (110) with respect to a surface of the edge and at a second oblique angle (114) with respect to an axis about which the rotor is circumscribed. Laser pulses form the elliptical shaped laser spots (60) that are angled from the leading edge (LE) radially inwardly towards the axis. In the exemplary embodiment, the elliptical shaped laser spots (60) have an overlap of about 50%.
The method includes continuously firing the stationary laser beam (102), which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges (LE, TE) of the blade (108), with the laser beam (102) compoundly angled such that it is aimed at a first oblique angle (110) with respect to a surface of the edge and at a second oblique angle (114) with respect to an axis about which the rotor is circumscribed. Laser pulses form the elliptical shaped laser spots (60) that are angled from the leading edge (LE) radially inwardly towards the axis. In the exemplary embodiment, the elliptical shaped laser spots (60) have an overlap of about 50%.
Claims (18)
1.A method for laser shock peening leading or trailing, edges (LE, TE) of gas turbine engine blades (108) mounted on a rotor element, said method comprising:
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blade with circular cross-section first and second laser beams (102, 104), firing the laser beams (102,104) at an oblique angle (110) with respect to the surfaces so as to form elliptical shaped laser spots (60) on the surfaces, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams (102) with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blade with circular cross-section first and second laser beams (102, 104), firing the laser beams (102,104) at an oblique angle (110) with respect to the surfaces so as to form elliptical shaped laser spots (60) on the surfaces, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams (102) with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
2.A method as claimed in claim 1 wherein the elliptical shaped laser spots (60) have major axis (64) extending away from the edge and over the surfaces and transverse minor axis (66) and the elliptical shaped laser spots (60) overlap by about 50%.
3. A method as claimed in claim 2 wherein the laser spots extend over the edge.
4. A method as claimed in claim 2 wherein relative movement between the laser beams (102,104) and the surfaces is effected while the laser beams are being fired.
5.A method for laser shock peening leading or trailing edges (LE, TE) of gas turbine engine blades mounted on a rotor element circumscribed about an axis of rotation (9) and having an annular space (13) between adjacent axially spaced apart forward and aft and rows of blades (12, 14), wherein the edges being laser shock peened border the space, said method comprising the following steps:
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blades in one of the rows with circular cross-section first and second laser beams (102,104) respectively, firing the laser beams at a first oblique angle (110) with respect to the surfaces so as to form elliptical shaped laser spots (60) on the surfaces and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blades in one of the rows with circular cross-section first and second laser beams (102,104) respectively, firing the laser beams at a first oblique angle (110) with respect to the surfaces so as to form elliptical shaped laser spots (60) on the surfaces and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
6.A method as claimed in claim 5 wherein the elliptical shaped laser spots (60) have major axis (64) extending away from the edge and over the surfaces and transverse minor axis (66) and the elliptical shaped laser spots (60) overlap by about 50%.
7. A method as claimed in claim 6 wherein the laser spots extend over the edge.
8. A method as claimed in claim 7 wherein relative movement between the laser beams and the surfaces is effected while the laser beams are being fired.
9.A method for laser shock peening leading or trailing edges (LE, TE) of gas turbine engine blades mounted on a rotor element, said method comprising:
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blade with circular cross-section first and second laser beams (102 and 104) respectively, firing the first laser beam (102) at an oblique angle (110) with respect to the pressure side surface (54) so as to form elliptical shaped laser spots (60) on the pressure side surface (54), firing the second laser beam (104) at about a normal angle with respect to the suction side surface (55) so as to form circular shaped laser spots (80) on the suction side surface (55), and overlapping adjacent elliptical shaped laser spots (60) and circular shaped laser spots (80) respectively and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peeving extending into the blade from the surfaces.
simultaneously laser shock peening pressure and suction side surfaces (54, 55) along one of the edges of the blade with circular cross-section first and second laser beams (102 and 104) respectively, firing the first laser beam (102) at an oblique angle (110) with respect to the pressure side surface (54) so as to form elliptical shaped laser spots (60) on the pressure side surface (54), firing the second laser beam (104) at about a normal angle with respect to the suction side surface (55) so as to form circular shaped laser spots (80) on the suction side surface (55), and overlapping adjacent elliptical shaped laser spots (60) and circular shaped laser spots (80) respectively and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peeving extending into the blade from the surfaces.
10.A method as claimed in claim 9 wherein the elliptical shaped laser spots (60) have major axis (64) extending away from the edge and over the surfaces and transverse minor axis (66) and the elliptical shaped laser spots (60) overlap by about 50%.
11. A method as claimed in claim 9 wherein the laser spots extend over the edge.
12. A method as claimed in claim 11 wherein relative movement between the laser beams and the surfaces is effected while the laser beams are being fired.
13.A method as claimed in claim 12 wherein the movement is linear to and at least one row of overlapping laser spots on each of the surfaces having generally equally spaced apart linearly aligned centerpoints (72).
14.A method for laser shock peeving leading or trailing edges (LE, TE) of gas turbine engine blades mounted on a rotor element circumscribed about an axis of rotation (9) and having an annular space (13) between adjacent axially spaced apart forward and aft and rows of blades (12, 14), wherein the edges being laser shock peened border the space, said method comprising the following steps:
simultaneously laser shock peeving pressure and suction side surfaces (54, 55) along one of the edges of the blades in one of the rows with circular cross-section first and second laser beams (102 and 104) respectively, firing the first laser beam (102) at a first oblique angle (110) with respect to the pressure side surface (54) so as to form elliptical shaped laser spots (60) on the pressure side surface (54) and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, firing the second first laser beam (104) at about a normal angle with respect to the suction side surface (55) so as to form circular shaped laser spots (80) on the suction side surface (55) and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
simultaneously laser shock peeving pressure and suction side surfaces (54, 55) along one of the edges of the blades in one of the rows with circular cross-section first and second laser beams (102 and 104) respectively, firing the first laser beam (102) at a first oblique angle (110) with respect to the pressure side surface (54) so as to form elliptical shaped laser spots (60) on the pressure side surface (54) and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, firing the second first laser beam (104) at about a normal angle with respect to the suction side surface (55) so as to form circular shaped laser spots (80) on the suction side surface (55) and at a second oblique angle (114) with respect the axis wherein the second oblique angle (114) is sufficient to clear blades in the adjacent row of blades, and overlapping adjacent elliptical shaped laser spots (60) and firing the laser beams with sufficient energy to form regions having compressive residual stresses imparted by the laser shock peening extending into the blade from the surfaces.
15.A method as claimed in claim 14 wherein the elliptical shaped laser spots (60) have major axis (64) extending away from the edge and over the surfaces and transverse minor axis (66) and the elliptical shaped laser spots (60) overlap by about 50%.
16. A method as claimed in claim 14 wherein the laser spots extend over the edge.
17. A method as claimed in claim 15 wherein the laser spots extend over the edge.
18. A method as claimed in claim l6 wherein relative movement between the laser beams and the surfaces is effected while the laser beams are being fired.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US09/771,856 US6541733B1 (en) | 2001-01-29 | 2001-01-29 | Laser shock peening integrally bladed rotor blade edges |
| US09/771,856 | 2001-01-29 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2368288A1 true CA2368288A1 (en) | 2002-07-29 |
| CA2368288C CA2368288C (en) | 2009-12-22 |
Family
ID=25093154
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002368288A Expired - Fee Related CA2368288C (en) | 2001-01-29 | 2002-01-17 | Laser shock peening integrally bladed rotor blade edges |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6541733B1 (en) |
| EP (1) | EP1227164B1 (en) |
| BR (1) | BR0200332B1 (en) |
| CA (1) | CA2368288C (en) |
| DE (1) | DE60233536D1 (en) |
| SG (1) | SG109489A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008010847A1 (en) * | 2008-02-25 | 2009-08-27 | Rolls-Royce Deutschland Ltd & Co Kg | Method and apparatus for shot peening of blisk blades |
| US8739589B2 (en) | 2010-01-27 | 2014-06-03 | Rolls-Royce Deutschland Ltd & Co Kg | Method and apparatus for surface strengthening of blisk blades |
| CN113426899A (en) * | 2021-06-25 | 2021-09-24 | 南通艾郎风电科技发展有限公司 | Laying method of wind power blades |
Families Citing this family (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6653755B2 (en) * | 2001-05-30 | 2003-11-25 | Intel Corporation | Radial air flow fan assembly having stator fins surrounding rotor blades |
| GB2398034B (en) | 2003-02-04 | 2005-08-10 | Rolls Royce Plc | Laser shock peening |
| US7097720B2 (en) * | 2003-04-30 | 2006-08-29 | General Electric Company | Lower fluence boundary laser shock peening |
| US6713716B1 (en) | 2003-05-30 | 2004-03-30 | General Electric Company | Reduced mist laser shock peening |
| US6917012B2 (en) * | 2003-07-03 | 2005-07-12 | General Electric Company | Reducing electromagnetic feedback during laser shock peening |
| US6900409B2 (en) * | 2003-08-22 | 2005-05-31 | General Electric Company | Single head laser high throughput laser shock peening |
| US20050194070A1 (en) * | 2004-03-02 | 2005-09-08 | Mannava Seetha R. | Lower fluence boundary oblique laser shock peening |
| WO2007055864A2 (en) * | 2005-10-12 | 2007-05-18 | Surface Technology Holdings, Ltd | Improved integrally bladed rotating turbo machinery and method and apparatus for achieving the same |
| US20070157447A1 (en) * | 2006-01-09 | 2007-07-12 | Prevey Paul S | Method of improving the properties of a repaired component and a component improved thereby |
| US8330070B2 (en) * | 2006-05-11 | 2012-12-11 | Kabushiki Kaisha Toshiba | Laser shock hardening method and apparatus |
| US20100136296A1 (en) * | 2006-11-30 | 2010-06-03 | United Technologies Corporation | Densification of coating using laser peening |
| US9133720B2 (en) * | 2007-12-28 | 2015-09-15 | United Technologies Corporation | Integrally bladed rotor with slotted outer rim |
| WO2013049797A1 (en) * | 2011-09-30 | 2013-04-04 | Fosdick George A | Wheel turbine rotor |
| US9533371B2 (en) | 2012-01-17 | 2017-01-03 | United Technologies Corporation | Apparatus and method for on line surface enhancement of a workpiece |
| WO2014055538A1 (en) | 2012-10-01 | 2014-04-10 | United Technologies Corporation | Methods for testing laser shock peening |
| CN103898297B (en) * | 2012-12-24 | 2016-07-06 | 中国科学院沈阳自动化研究所 | A kind of blisk laser shock peening method |
| US11047017B2 (en) | 2014-09-09 | 2021-06-29 | G.C. Laser Systems, Inc. | Laser ablation devices that utilize beam profiling assemblies to clean and process surfaces |
| US9914985B2 (en) * | 2014-09-09 | 2018-03-13 | G.C. Laser Systems, Inc. | Laser ablation and processing methods and systems |
| CN106282532B (en) * | 2016-08-18 | 2018-01-16 | 江苏大学 | A kind of laser impact intensified combined method for obtaining metal surface crystal grain mixed distribution |
| CN106467933B (en) * | 2016-08-29 | 2018-10-09 | 江苏大学 | A kind of laser shock peening method based on gradient crystal grain |
| US11298799B2 (en) * | 2018-05-03 | 2022-04-12 | General Electric Company | Dual sided shot peening of BLISK airfoils |
| CN111575476B (en) * | 2020-04-09 | 2021-10-26 | 广东镭奔激光科技有限公司 | Laser shock peening method for blade edge |
| LU102198B1 (en) * | 2020-11-05 | 2022-05-05 | Centrum Vyzkumu Rez S R O | A method for extending a fatigue life of a turbine blade affected by pitting and product thereof |
| CN114250356B (en) * | 2021-12-16 | 2023-08-29 | 江苏大学 | Method for improving fatigue performance of fiber metal laminate mechanical connector |
| CN114592119A (en) * | 2022-03-14 | 2022-06-07 | 中国航空制造技术研究院 | Laser shock peening method based on prestress |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2724003B2 (en) | 1989-11-10 | 1998-03-09 | キヤノン株式会社 | Magneto-optical recording medium |
| US5067876A (en) | 1990-03-29 | 1991-11-26 | General Electric Company | Gas turbine bladed disk |
| WO1994014811A1 (en) | 1992-12-21 | 1994-07-07 | Chong Kun Dang Corp. | 2-(2-substituted pyrrolidin-4-yl)thio-carbapenem derivatives |
| US5492447A (en) | 1994-10-06 | 1996-02-20 | General Electric Company | Laser shock peened rotor components for turbomachinery |
| US5591009A (en) | 1995-01-17 | 1997-01-07 | General Electric Company | Laser shock peened gas turbine engine fan blade edges |
| US5674329A (en) | 1996-04-26 | 1997-10-07 | General Electric Company | Adhesive tape covered laser shock peening |
| US5674328A (en) | 1996-04-26 | 1997-10-07 | General Electric Company | Dry tape covered laser shock peening |
| US5911890A (en) | 1997-02-25 | 1999-06-15 | Lsp Technologies, Inc. | Oblique angle laser shock processing |
| US5932120A (en) | 1997-12-18 | 1999-08-03 | General Electric Company | Laser shock peening using low energy laser |
| US5951790A (en) * | 1998-06-26 | 1999-09-14 | General Electric Company | Method of monitoring and controlling laser shock peening using an in plane deflection test coupon |
| US6183882B1 (en) * | 1998-06-29 | 2001-02-06 | General Electric Company | In plane deflection coupon for monitoring and controlling of laser shock peening |
| US6200689B1 (en) * | 1998-10-14 | 2001-03-13 | General Electric Company | Laser shock peened gas turbine engine seal teeth |
| US5948293A (en) * | 1998-12-03 | 1999-09-07 | General Electric Company | Laser shock peening quality assurance by volumetric analysis of laser shock peened dimple |
| US6296448B1 (en) * | 1999-09-30 | 2001-10-02 | General Electric Company | Simultaneous offset dual sided laser shock peening |
-
2001
- 2001-01-29 US US09/771,856 patent/US6541733B1/en not_active Expired - Fee Related
-
2002
- 2002-01-17 CA CA002368288A patent/CA2368288C/en not_active Expired - Fee Related
- 2002-01-29 EP EP02250594A patent/EP1227164B1/en not_active Expired - Lifetime
- 2002-01-29 DE DE60233536T patent/DE60233536D1/en not_active Expired - Lifetime
- 2002-01-29 BR BRPI0200332-5A patent/BR0200332B1/en not_active IP Right Cessation
- 2002-01-29 SG SG200200529A patent/SG109489A1/en unknown
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008010847A1 (en) * | 2008-02-25 | 2009-08-27 | Rolls-Royce Deutschland Ltd & Co Kg | Method and apparatus for shot peening of blisk blades |
| US8256117B2 (en) | 2008-02-25 | 2012-09-04 | Rolls-Royce Deutschland Ltd & Co Kg | Method for the controlled shot peening of blisk blades wherein a shot peening stream is provided on a pressure and a suction side of the blades |
| US8739589B2 (en) | 2010-01-27 | 2014-06-03 | Rolls-Royce Deutschland Ltd & Co Kg | Method and apparatus for surface strengthening of blisk blades |
| CN113426899A (en) * | 2021-06-25 | 2021-09-24 | 南通艾郎风电科技发展有限公司 | Laying method of wind power blades |
| CN113426899B (en) * | 2021-06-25 | 2024-03-08 | 南通艾郎风电科技发展有限公司 | Wind power blade laying method |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1227164A3 (en) | 2003-11-26 |
| BR0200332B1 (en) | 2012-01-24 |
| BR0200332A (en) | 2002-10-29 |
| CA2368288C (en) | 2009-12-22 |
| EP1227164A2 (en) | 2002-07-31 |
| US6541733B1 (en) | 2003-04-01 |
| SG109489A1 (en) | 2005-03-30 |
| EP1227164B1 (en) | 2009-09-02 |
| DE60233536D1 (en) | 2009-10-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20160118 |